Erik Lapkhanov

@itm.dp.ua

Department of system analysis and control problems
Institute of technical mechanics of National academy of science of Ukraine and State space agency of Ukraine

Erik Lapkhanov


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https://researchid.co/erik__lapkh

EDUCATION

1) National Aerospace University “Kharkov aviation institute” – Bachelor’s Degree. Specialty: Automation and Computer-Integrated Technologies. Qualification: Technical expert in physical sciences and technology. Diploma with Honour (2010 -2014).
2) National Aerospace University “Kharkov aviation institute” – Master’s Degree. Specialty: Automation and Computer-Integrated Technologies. Qualification: Research engineer in automation and computer-integrated technologies, computing systems designer. Diploma with Honour (2014-2016).
3) Oles Honchar Dnipro National University, Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine (dual education) – Ph. D. in automation and instrumentation. Specialty: Automation and Computer-Integrated Technologies (Dynamics, ballistics and spacecraft control). (2016-2021)

RESEARCH INTERESTS

Dynamics, ballistics and spacecraft control
Automation and instrumentation, applied mathematics, control systems
13

Scopus Publications

122

Scholar Citations

7

Scholar h-index

4

Scholar i10-index

Scopus Publications

  • Methodology for a priori stability analysis of a distributed orbital sunshade system
    Anatolii Alpatov, Erik Lapkhanov
    Advances in Space Research, 2026
  • ESTIMATING THE DEGREE OF DISPOSAL OF A LAUNCH VEHICLE CASING MADE FROM POLYOLEFINS IN THE EARTH’S ATMOSPHERE
    Mykola Dron, Erik Lapkhanov, Aleksandr Golubek, Andrii Dreus, Olena Kositsyna, et al.
    Eastern European Journal of Enterprise Technologies, 2025
    The object of this study is the process of disposing of the upper stage body of a launch vehicle made of polyolefins by burning in the dense layers of the Earth’s atmosphere during removal from Earth orbit. The task addressed was to determine the possibility of disposal of the upper stage bodies of launch vehicles made of polyolefins during deorbiting. The mathematical model built makes it possible to take into account the effect of ballistic and aerothermodynamic aspects at the same time. The application of this model makes it possible to estimate the degree of disposal of the upper stage bodies of launch vehicles made of polyolefins in the Earth’s atmosphere at the stage of scientific research. In turn, this makes it possible to rationally choose the design parameters of materials for launch vehicle bodies, taking into account the disposal phase in the dense layers of the atmosphere, as well as rationally select the initial parameters for deorbiting orbits. This makes it possible to maximize the level of disposal and minimize the probability of debris falling on uninhabited areas of the Earth. The results of the study showed that launch vehicle bodies made of polymer materials such as polyethylene and polypropylene could burn up in the atmospheric part of the trajectory by 90–100 %, depending on the mass-dimensional characteristics and the type of orbit. In turn, increasing the ellipticity of the orbit makes it possible to increase the steepness of the entry of the upper body of the launch vehicle into the dense layers of the atmosphere, and hence, to increase the heat flows that contribute to the combustion of the body. With this in mind, methodological recommendations have been compiled for choosing orbits of the necessary ellipticity, taking into account the place of fall of fragments of the upper bodies of carrier rockets that did not burn up in the atmosphere
  • ORBIT SELECTION OF THE SPACE INDUSTRIAL PLATFORM WITH DISTRIBUTED ELECTRICAL-POWER SYSTEM MODULES
    , A. ALPATOV, , C. WANG, , H. LU, , , E. LAPKHANOV, and
    Space Science and Technology, 2024
    Space industrialization is one of the prospective directions in modern aerospace science and engineering for space exploration of new resources and habitats. The key issue is to provide industrial space modules with the required amount of electricity needed. One type of power supply for such modules is the use of distributed power systems, which consist of constellations of spacecraft with contactless power transmission. Given this, the problem of rational orbit selection for their dislocation arises. Considering these problems, the methodology for orbits selection of the space industrial platform with distributed electrical-power system modules is proposed in the paper. This methodology includes orbital translation, attitude, relative dynamics estimation for each power satellite, and its corresponding orbit optimization algorithm. The orbit optimization algorithm includes statistical processing and elements of gradient and coordinate descent methods, allowing us to determine the most significant parameter influencing the duration of the contactless power transmission session. Also, quaternion mathematics is used to estimate the dynamics in the program parameters for targeting the transmitter spacecraft antenna to the receiver spacecraft rectenna. With the approaches mentioned above, the methodology proposed in this paper allows us to form the requirements for the power satellites’ attitude and orbit control system to improve the process of selecting corresponding design parameters of such systems. Thus, the usage of the proposed methodology can allow the designing of the power satellites’ attitude and orbit control system in the conceptual stages of designing.
  • Combined method for spacecraft deorbiting with angular stabilization of the sail using magnetorquers
    Anatoliy Alpatov, Mykola Dron’, Aleksandr Golubek, Erik Lapkhanov
    Ceas Space Journal, 2023
  • DEVELOPMENT AND JUSTIFICATION OF THE SYSTEM METHODOLOGICAL APPROACH TO ASSESSING THE INVESTMENT BUSINESS PROJECT IMPLEMENTATION EFFICIENCY UNDER CONDITIONS OF THE EXTERNAL MARKET ENVIRONMENT FACTORS IMPACT
    Dmytro Kabachenko, Erik Lapkhanov
    Eastern European Journal of Enterprise Technologies, 2023
    Evaluating the effectiveness of the implementation of an investment project is a key issue when making management decisions both at the stage of setting up a startup and for expanding an existing business. This paper reports a systematic approach to building a mathematical model to solve the task of forecasting the effectiveness of business projects, taking into account the influence of factors of the external economic environment. Proposed factors include the impact of supply and demand on the price of goods, political and industry risks, the volume of commodity supply and sales. In view of this, a method for calculating the political component of the discount coefficient using the Fourier series has been proposed. Using the theory of differential equations, correlation and regression analysis, a mathematical model for forecasting indicators of efficiency of business project implementation taking into account the influence of factors of the external economic environment has been constructed. Based on it, a generalized algorithm for applying a mathematical model to predict the effectiveness of investment projects in various business sectors has been developed. The results from applying differential equations and variable discount coefficient showed a decrease in NPV by 14 %, and PI by 5.1 %, due to more accurate consideration of the political component in calculating the discount factor. Also, with the influence of supply and demand on the price of goods and nonlinear cash flows, it was found that the payback period does not clearly indicate the effectiveness of the implementation of an investment business project. Determining these factors provides more accurate information to the investor or business owner when forecasting the stability of a business project for making management decisions on its implementation
  • DEVELOPMENT OF THE METHODOLOGICAL APPROACHES FOR THE ATTITUDE CONTROL SYSTEM OF THE EARTH REMOTE SENSING SATELLITE IN THE CONDITIONS OF THE ONBOARD EQUIPMENT PARTIAL FAILURES
    Petro Zheliabov, Erik Lapkhanov
    Eureka Physics and Engineering, 2022
    The spacecraft controllability of the angular motion is possible only with operability of the attitude and orbit control system (AOCS) of the spacecraft, sensors, actuators and the spacecraft power system. However, there is a rather significant probability of failure of this equipment during the operation of the spacecraft. This is especially observed after half of the spacecraft's lifetime or because of emergency situations. There is a problem which is connected with providing the maximum performance of the AOCS in case of partial failures of their actuators (reaction wheels (RW), magnetorquer rods (MGTR), etc.).
 Thus, the purpose of this work is the development and synthesis of special algorithms for spacecraft angular motion control in the emergency situations which are connected with RWs partial failures and restrictions of onboard electricity consumption. The approach of synthesis of this control algorithms is based on using mobile control methods which allow to reserve RWs by MGTRs. There are different variants of control loops depending on MGTRs turning on combinations. There were proposed two types of control switching functions: time-periodic and switching by deviation. Also was proposed a methodology of controller synthesis using these switching functions.
 Using this methodology and computer simulation, it was shown the possibility of providing angular nadir orientation and stabilization of the spacecraft with maximum 1−1.5 deg error in case of time-periodic switching functions implementation. Switching by deviation allows to reduce onboard electricity consumption for 25−30 % comparing with using time-periodic switching. However, the accuracy of stabilization significantly lower in case of switching by deviation. Considering these estimates, the corresponding methodological recommendations were formulated for use switching functions depending on emergency
  • TIME-PERIODIC SPACECRAFT ATTITUDE CONTROL WITH THE USE OF SLEWING PERMANENT MAGNETS
    S. Khoroshylov, E. Lapkhanov
    Science and Innovation, 2022
    Introduction. Electromagnetic actuators are widely used in spacecraft (SC) attitude control systems. These actuators can be modified by using slewing permanent magnets (ASPM) as sources of torque instead of electromagnets. These modified devices consume less onboard electricity for SC attitude control than the conventional ones.Problem Statement. An algorithm for attitude stabilization of a SC using ASPM was proposed in previous studies, where the pole placement technique and pulse-width modulation (PWM) were used to design the controller. However, this approach does not allow the designers to find optimal values of the required magnetic torques, which may result in frequent engagement of the stepper motors of the ASPMs and their significant energy consumption. This controller has such a drawback because its gains are selected without taking into account time-periodic properties of the Earth magnetic field.Purpose. The purpose of the study is to design the algorithm for the SC angular stabilization by the ASPMs taking into account time-periodic properties of the Earth magnetic field.Materials and Methods. The solution of the time-periodic Riccati equation was used for the controller design. Mathematical modeling and computer simulation of SC motion was applied to build the model of the plan and validate the results.Results. A time-periodic based SC attitude control algorithm has been designed. Taking into consideration the time-periodic properties of the magnetic field of Earth allow us to optimize the required magnetic control torques. This algorithm minimizes the frequency of the actuation of the ASPM sashes, and thus reduces onboard energy consumption.Conclusions. The designed algorithm increases the control efficiency of SC attitude control by using jointly the ASPMs, time-periodic linear-quadratic regulator and pulse-width modulator.
  • DESIGNING the CONFIGURATION and SELECTING the DESIGN PARAMETERS of DRAG SYSTEMS for DEORBITING SPACECRAFT CREATED by PIVDENNE DESIGN OFFICE
    А. Алпатов, Е. Лапханов, О. Палій
    Science and Innovation, 2022
    Вступ. Для стабілізації середовища космічного сміття відпрацьовані космічні апарати та верхні ступені ракет-носіїв необхідно відводити з орбіти.Проблематика. Проведений аналіз надувних аеродинамічних систем відведення космічних апаратів з орбіти показав, що вони є ефективним засобом відведення космічних апаратів з орбіти на висотах до 800 км, однак мають певні недоліки: ймовірність пошкодження фрагментами космічного сміття через чутливість матеріалу оболонки, а також ймовірність електростатичного пробою.Мета. Розробка конструктивної схеми та вибір параметрів аеродинамічної системи відведення космічних апаратів, розроблених ДП «КБ «Південне», з орбіти.Матеріали й методи. Методи механіки космічного польоту, математичне моделювання задач проєктування.Результати. Розрахунки показали, що час відведення космічного апарату «Січ-2-1» із планованої орбіти складає близько 6,5 років при масі аеродинамічної системи відведення 9 кг, що складає 5% від маси зазначеного космічного апарата. Визначено, що у разі збільшення часу відведення космічного апарата «Січ-2-1» з планованої орбіти після завершення експлуатації до 25 років, масу аеродинамічної системи можна зменшити до 4,5 кг. При масі аеродинамічної системи відведення в 9 кг, межею ефективного застосування зазначеної аеродинамічної системи відведення є висоти від 730 до 750 км на близьких до кругових орбітах різної дислокації і висоти не більше 700 км в перигеї та 842 км в апогеї на малоеліптичних орбітах.Висновки. Виходячи із вимог ДП КБ «Південне» до масових і габаритних параметрів засобу відведення, було розроблено конструктивну схему і проєктний вигляд аеродинамічної системи відведення, що розгортається. Особливістю конструкції є компактність, що забезпечується застосуванням пружинних механізмів і маловитратних мікроелектродвигунів, що розгортають аеродинамічні елементи. Така конструкція займає незначний об’єм на космічному апараті «Січ-2-1»
  • DETERMINING THE DEGREE OF EFFECT OF HEAT FLOWS ON THE DEFORMATION OF THE SHELL OF A SPACE INFLATABLE PLATFORM WITH A PAYLOAD
    Erik Lapkhanov, Oleksandr Palii, Aleksandr Golubek
    Eastern European Journal of Enterprise Technologies, 2022
    This paper reports a study into the influence exerted by the thermal flows of space environment on the deformation of the shell of a space inflatable platform with a payload. The mathematical model of the effect of temperature fluctuations on the mass-inertial characteristics of the space inflatable platform of an ellipsoidal shape has been improved. The following assumptions were introduced to the model. The temperature distribution on the illuminated part and the unlit part of the shell is uniform. The gradient of the temperature difference between the illuminated and unlit parts is the same for all points of the shell. To determine deformations, a moment-free theory was used. The model of the space inflatable platform is a «rubber bullet» that works only for stretching and compression. All deformations are elastic. The advantages and limitations of the use of the developed mathematical model have been determined. Computer simulation of the orbital motion of a space inflatable platform with a payload in a sun-synchronous orbit was carried out. The material of the platform shell is Kapton. Estimates of temperature fluctuations in the illuminated and unlit part of the shell and the temperature of the gas inside it were obtained. The dependence of elastic deformations on temperature was determined, taking into account the Young’s modulus of the material. The influence of changes in gas pressure on the movement of payload attachment points and the change in the inertia tensor have been determined. The obtained results showed that the inertia tensor varies within the order of 10–5 kgm2. The maximum deviation of the fastening points of the payload from the initial position on the illuminated part of the shell was about 10–6 m. Considering the stability of the structure to the effects of heat flows of the space environment, the possibility of using space inflatable platforms as a means for separating a grouping of satellites has been shown
  • DEVELOPMENT OF R&D FRAMEWORK FOR THE MODERNIZATION OF THE AERODYNAMIC DEORBIT SYSTEM FOR THE USE IN THE UPPER STAGE OF CYCLONE-1M LAUNCH VEHICLE
    А. Алпатов, О. Кузнецов, О. Палій, Е. Лапханов
    Science and Innovation, 2022
    Вступ. Зростання інтересу до освоєння космічного простору та нові технології супутникової навігації та зв’язку призвели до збільшення кількості космічних апаратів (КА) на навколоземних орбітах і створення орбітальних угрупувань. На сьогодні головним засобом, що здійснює виведення КА на навколоземні орбіти, є ракети-носії, відпрацьовані верхні ступені яких, після виведення КА, залишаються на навколоземних орбітах і уворюють космічне сміття (КС).Проблематика. Проблема зростання кількості КС є однією із ключових у сучасній космонавтиці. Значне накопичення фрагментів КС на деяких кластерах орбіт може чинити значні перешкоди діючим КА, а також призвести до глобальних проблем — ефекту Кеслера. Одним із джерел зростання КС є відпрацьовані верхні ступені ракет-носіїв (РН). Розробка засобів відведення верхніх ступенів РН з навколоземних орбіт є актуальною, а проєкт РН легко класу «Циклон-1М» розробки ДП «КБ «Південне» ім. М. К. Янгеля» є однією з перспективних розробок.Мета. Розробка науково-технічного забезпечення модернізації аеродинамічної системи відведення для використання на верхньому ступені ракети-носія «Циклон-1М».Матеріали й методи дослідження. Застосовано методи прикладної механіки, математичного й комп’ютерного моделювання руху космічних апаратів.Результати. Розроблено науково-технічне забезпечення для створення нової аеродинамічної системи відведення (АСВ) верхнього ступеня РН «Циклон-1М». Створено нову конструкцію аеродинамічного елементу АСВ у формі трьох ортогонально розміщених круглих дисків, що дозволяє підвищити ефективність застосування АСВ. Запропоновано конструктивну схему та технологію виготовлення контейнера для зберігання АСВ на верхньому ступені РН «Циклон-1М» з використанням сотових технологій, що дозволяє мінімізувати масу системи.Висновки. Технічний результат запропонованої розробки демонструє збільшення ефективності застосування АСВ при неорієнтованому кутовому русі під час відведення РН та дозволяє зменшити масу системи зберігання.
  • Electromagnetic Stabilization System Algorithm During Energy Restriction Mode for the Near-Symmetric Satellites
    Petr Zheliabov, Erik Lapkhanov, Dmytro Faizullin, Anatoliy Kulabukhov, Koju Hiraki
    International Review of Aerospace Engineering, 2022
  • Synthesizing an algorithm to control the angular motion of spacecraft equipped with an aeromagnetic deorbiting system
    Anatolii Alpatov, Serhii Khoroshylov, Erik Lapkhanov
    Eastern European Journal of Enterprise Technologies, 2020
  • Development of the aeromagnetic space debris deorbiting system
    Erik Lapkhanov, Serhii Khoroshylov
    Eastern European Journal of Enterprise Technologies, 2019

RECENT SCHOLAR PUBLICATIONS

  • Methodology for a priori stability analysis of a distributed orbital sunshade system
    A Alpatov, E Lapkhanov
    Advances in Space Research , 2026
    2026
  • PROBLEM OF DEVELOPING AND MAKING SPACE SYSTEMS TO REDUCE THE SOLAR RADIATION INCIDENT ON THE EARTH’S SURFACE
    EO LAPKHANOV
    Technical Mechanics, 52-62 , 2025
    2025
    Citations: 1
  • ESTIMATING THE DEGREE OF DISPOSAL OF A LAUNCH VEHICLE CASING MADE FROM POLYOLEFINS IN THE EARTH’S ATMOSPHERE.
    MA Dron, E Lapkhanov, A Golubek, A Dreus, O Kositsyna, L Dubovik
    Eastern-European Journal of Enterprise Technologies 133 (1) , 2025
    2025
    Citations: 1
  • ESTIMATING THE DEGREE OF DISPOSAL OF A LAUNCH VEHICLE CASING MADE FROM POLYOLEFINS IN THE EARTH’S ATMOSPHERE
    E Lapkhanov, A Golubek, A Dreus, O Kositsyna, L Dubovik
    2025
  • PECULIARITIES OF THE NET PRESENT VALUE AND PROFIT INDEX CALCULATIONS USING CONTINIOUS FUNCTIONS AND DIFFERENTIAL EQUATIONS MODELS
    E Lapkhanov, D Kabachenko
    Publishing House “Baltija Publishing” , 2024
    2024
    Citations: 4
  • TRADITIONAL AND INNOVATIVE APPROACHES IN ECONOMICS: THEORY, METHODOLOGY, PRACTICE
    O Bykonia, N Romanovska, L Venger, V Blyzniuk, L Yatsenko, L Bogush, ...
    2024
  • ORBIT SELECTION OF THE SPACE INDUSTRIAL PLATFORM WITH DISTRIBUTED ELECTRICAL-POWER SYSTEM MODULES
    A ALPATOV, C WANG, H LU, E LAPKHANOV
    КОСМИЧЕСКАЯ НАУКА И ТЕХНОЛОГИЯ 30 (4), 03-23 , 2024
    2024
  • DEVELOPMENT AND JUSTIFICATION OF THE SYSTEM METHODOLOGICAL APPROACH TO ASSESSING THE INVESTMENT BUSINESS PROJECT IMPLEMENTATION EFFICIENCY UNDER CONDITIONS OF THE EXTERNAL …
    D Kabachenko, E Lapkhanov
    Eastern-European Journal of Enterprise Technologies 123 (3) , 2023
    2023
    Citations: 5
  • On the issue of creating space based shading and lighting systems for earth surface
    AP Alpatov, EO Lapkhanov
    Технічна механіка, 25-39 , 2023
    2023
    Citations: 1
  • РОЗРОБКА НАУКОВО-ТЕХНІЧНОГО ЗАБЕЗПЕЧЕННЯ МОДЕРНІЗАЦІЇ АЕРОДИНАМІЧНОЇ СИСТЕМИ ВІДВЕДЕННЯ ДЛЯ ВИКОРИСТАННЯ НА ВЕРХНЬОМУ СТУПЕНІ РАКЕТИ-НОСІЯ «ЦИКЛОН-1М»
    A Alpatov, O Kuznetsov, O Palii, Е Lapkhanov
    Science and Innovation 18 (6), 60-71 , 2022
    2022
  • DETERMINING THE DEGREE OF EFFECT OF HEAT FLOWS ON THE DEFORMATION OF THE SHELL OF A SPACE INFLATABLE PLATFORM WITH A PAYLOAD.
    E Lapkhanov, O Palii, A Golubek
    Eastern-European Journal of Enterprise Technologies 119 (1) , 2022
    2022
    Citations: 3
  • Development of the methodological approaches for the attitude control system of the Earth remote sensing satellite in the conditions of the onboard equipment partial failures
    P Zheliabov, E Lapkhanov
    EUREKA: Physics and Engineering, 77-90 , 2022
    2022
    Citations: 1
  • Time-Periodic Spacecraft Attitude Control with the Use of Slewing Permanent Magnets
    S Khoroshylov, E Lapkhanov
    Science and innovation 18 (5), 38-48 , 2022
    2022
    Citations: 1
  • Model of distributed space power system motion control
    OS Palii, EO Lapkhanov, DS Svorobin
    Space , 2022
    2022
    Citations: 5
  • РОЗРОБКА КОНСТРУКТИВНОЇ СХЕМИ ТА ВИБІР ПАРАМЕТРІВ АЕРОДИНАМІЧНОЇ СИСТЕМИ ВІДВЕДЕННЯ КОСМІЧНИХ АПАРАТІВ РОЗРОБКИ ДП КБ «ПІВДЕННЕ» З ОРБІТИ
    A Alpatov, Е Lapkhanov, O Palii
    Science and Innovation 18 (4), 55-63 , 2022
    2022
  • Verification of analytical antiderivatives forms using correlation analysis for mechanical problems
    AР Alpatov, V KRAVETS, V KRAVETS, E LAPKHANOV
    Технічна механіка, 26-35 , 2022
    2022
  • Designing the configuration and selecting the design parameters of drag systems for deorbiting spacecraft created by pivdenne design office
    AP Alpatov, EO Lapkhanov
    Science and innovation, 55-63 , 2022
    2022
    Citations: 1
  • Development of R&D Fra-mework for the Modernization of the Aerodynamic Deorbit System for the Use in the Upper Stage of Cyclone-1M Launch Vehicle
    AP Alpatov, OP Kuznetsov, OS Palii, EO Lapkhanov
    Science and innovation, 60-71 , 2022
    2022
    Citations: 1
  • Electromagnetic Stabilization System Algorithm During Energy Restriction Mode for the Near-Symmetric Satellites
    P Zheliabov, A Kulabukhov, E Lapkhanov, D Faizullin, K Hiraki
    International Review of Aerospace Engineering 15 (1), 62-70 , 2022
    2022
    Citations: 4
  • Algorithm for the Set of Similarity Criteria Formation for a Physical Process in the Class of Homogeneous Functions
    A Alpatov, V Kravets, D Kolosov, V Kravets, E Lapkhanov
    2021

MOST CITED SCHOLAR PUBLICATIONS

  • Development of the aeromagnetic space debris deorbiting system
    E Lapkhanov, S Khoroshylov
    Eastern-European Journal of Enterprise Technologies 5 (5), 30-37 , 2019
    2019.0
    Citations: 22
  • Synthesizing an algorithm to control the angular motion of spacecraft equipped with an aeromagnetic deorbiting system
    A Alpatov, S Khoroshylov, E Lapkhanov
    Восточно-Европейский журнал передовых технологий 1 (5), 37-46 , 2020
    2020.0
    Citations: 15
  • Features of the development of means for spacecraft removal from near-Earth op-erational orbits
    EO Lapkhanov
    Technology 15 (2), 79-89 , 2019
    2019.0
    Citations: 13
  • Analiz mozhly-vosti zastosuvannya dvygunnoyi ustanovkyz postij-nymymagnitamydlya kosmichnyx aparativ na navkolozemnij orbiti [The analysis of the possibility of using an …
    EO Lapkhanov, OS Palij
    Systemni texnologiyi–System technologies, 117 , 2018
    2018.0
    Citations: 10
  • Analysis of technologies for spacecraft removal from Low Earth Orbits using onboard-produced electromagnetic and magnetic fields
    E Lapkhanov, A Paliy
    Техническая механика 4, 21-29 , 2018
    2018.0
    Citations: 9
  • Combined method for spacecraft deorbiting with angular stabilization of the sail using magnetorquers. CEAS Space J. 2022. No. 4
    A Alpatov, GA Dron’M, E Lapkhanov
    Citations: 9
  • The use of mobile control methods for stabilization of a spacecraft with aeromagnetic deorbiting system
    A Alpatov, E Lapkhanov
    Системні технології 6 (125), 41-54 , 2019
    2019.0
    Citations: 7
  • DEVELOPMENT AND JUSTIFICATION OF THE SYSTEM METHODOLOGICAL APPROACH TO ASSESSING THE INVESTMENT BUSINESS PROJECT IMPLEMENTATION EFFICIENCY UNDER CONDITIONS OF THE EXTERNAL …
    D Kabachenko, E Lapkhanov
    Eastern-European Journal of Enterprise Technologies 123 (3) , 2023
    2023.0
    Citations: 5
  • Model of distributed space power system motion control
    OS Palii, EO Lapkhanov, DS Svorobin
    Space , 2022
    2022.0
    Citations: 5
  • Representation of the kinematics of the natural trihedral of a spiral-helix trajectory by quaternion matrices
    A Alpatov, K Vic, K Vol, E Lapkhanov
    Transactions on Machine Learning and Artificial Intelligence 9 (4), 18-29 , 2021
    2021.0
    Citations: 5
  • PECULIARITIES OF THE NET PRESENT VALUE AND PROFIT INDEX CALCULATIONS USING CONTINIOUS FUNCTIONS AND DIFFERENTIAL EQUATIONS MODELS
    E Lapkhanov, D Kabachenko
    Publishing House “Baltija Publishing” , 2024
    2024.0
    Citations: 4
  • Electromagnetic Stabilization System Algorithm During Energy Restriction Mode for the Near-Symmetric Satellites
    P Zheliabov, A Kulabukhov, E Lapkhanov, D Faizullin, K Hiraki
    International Review of Aerospace Engineering 15 (1), 62-70 , 2022
    2022.0
    Citations: 4
  • DETERMINING THE DEGREE OF EFFECT OF HEAT FLOWS ON THE DEFORMATION OF THE SHELL OF A SPACE INFLATABLE PLATFORM WITH A PAYLOAD.
    E Lapkhanov, O Palii, A Golubek
    Eastern-European Journal of Enterprise Technologies 119 (1) , 2022
    2022.0
    Citations: 3
  • Особливості застосування магнітних органів керування для здійснення грубої стабілізації космічних апаратів з аеромагнітними системами відведення
    ЕО Лапханов
    Технічна механіка, 56-66 , 2020
    2020.0
    Citations: 2
  • PROBLEM OF DEVELOPING AND MAKING SPACE SYSTEMS TO REDUCE THE SOLAR RADIATION INCIDENT ON THE EARTH’S SURFACE
    EO LAPKHANOV
    Technical Mechanics, 52-62 , 2025
    2025.0
    Citations: 1
  • ESTIMATING THE DEGREE OF DISPOSAL OF A LAUNCH VEHICLE CASING MADE FROM POLYOLEFINS IN THE EARTH’S ATMOSPHERE.
    MA Dron, E Lapkhanov, A Golubek, A Dreus, O Kositsyna, L Dubovik
    Eastern-European Journal of Enterprise Technologies 133 (1) , 2025
    2025.0
    Citations: 1
  • On the issue of creating space based shading and lighting systems for earth surface
    AP Alpatov, EO Lapkhanov
    Технічна механіка, 25-39 , 2023
    2023.0
    Citations: 1
  • Development of the methodological approaches for the attitude control system of the Earth remote sensing satellite in the conditions of the onboard equipment partial failures
    P Zheliabov, E Lapkhanov
    EUREKA: Physics and Engineering, 77-90 , 2022
    2022.0
    Citations: 1
  • Time-Periodic Spacecraft Attitude Control with the Use of Slewing Permanent Magnets
    S Khoroshylov, E Lapkhanov
    Science and innovation 18 (5), 38-48 , 2022
    2022.0
    Citations: 1
  • Designing the configuration and selecting the design parameters of drag systems for deorbiting spacecraft created by pivdenne design office
    AP Alpatov, EO Lapkhanov
    Science and innovation, 55-63 , 2022
    2022.0
    Citations: 1